CN115828458A

CN115828458A - Design and optimization method of aeroengine precision small-allowance blade correction die

Info

Publication number: CN115828458A
Application number: CN202211502087.3A
Authority: CN
Inventors: 叶伟; 邓凯; 丁贵乐; 吴健; 谢少光
Original assignee: AECC Guizhou Liyang Aviation Power Co Ltd
Current assignee: AECC Guizhou Liyang Aviation Power Co Ltd
Priority date: 2022-11-28
Filing date: 2022-11-28
Publication date: 2023-03-21

Abstract

The invention discloses a design and optimization method of a precise small-allowance blade correcting die of an aircraft engine, which is characterized in that on the basis of qualified finish forging dies, forging rebound deformation pre-torsion angle compensation of each section blade body molded line of the finish forging die is cancelled, a trimming die is designed, the pre-torsion angle compensation of each section blade body molded line is reduced to 1/2 of the original size, a 1 st version correcting die is formed, a forge piece is heated, corrected and pressure tested, the torsion angle deviation of the size of each section of the forge piece after the pressure test and the theoretical size and the contour deviation after torsion angle fitting are measured, according to the torsion angle deviation, the correcting die molded line correspondingly rotates, points are taken on a single spline curve of the section molded line of the correcting die according to equal arc length, the coordinates of the points are output, the coordinates are adjusted according to the contour deviation, a new spline curve is made after adjustment and smooth, the design of the 2 nd version correcting die is completed, and the steps are repeated until the corrected size reaches the requirement. The invention improves the dimensional accuracy of the small-allowance blade correcting piece, does not need die repairing and improves the production efficiency.

Description

Design and optimization method of aeroengine precision small-allowance blade correction die

Technical Field

The invention belongs to the technical field of aeroengine blade correcting dies, and particularly relates to a design and optimization method of an aeroengine precision small-allowance blade correcting die.

Background

The size control requirement of the blade forging of the aircraft engine is high, and particularly for the precise small-allowance blade (the small allowance is 0.2-0.5 mm of machining allowance), the size of the forging is corrected to be used as a final forging process, and the size of the forging plays a key role. In the thermal correction process, the deformation of the forge piece is very small, the forge piece has local plastic deformation and elastic deformation, and the size control difficulty is high.

At present, the traditional correction die designed by adopting the theoretical modeling of the forge piece is only suitable for the forge piece with large allowance, and when the correction die is used for correcting the forge piece with small precision allowance, the local allowance of the forge piece is smaller or even has no allowance due to the plastic deformation and the elastic deformation of the forge piece.

Disclosure of Invention

The invention aims to provide a design and optimization method of a precise small-allowance blade correcting die of an aero-engine, which solves the problem of influence of local plastic deformation and elastic deformation on the size when a precise small-allowance blade forging is corrected, and accurately controls the size of the forging.

The technical scheme of the invention is as follows:

the design and optimization method of the aeroengine precision small margin blade correcting die comprises the following steps,

step 1, designing a trimming die on the basis of qualified finish forging dies, and specifically comprising the following steps:

step 1.1, canceling the compensation of forging rebound deformation pre-torsion angle of each section blade profile of the finish forging die;

step 1.2, making a trimming die on the basis of a finish forging die by utilizing Boolean operation, and trimming the finish forging by using the trimming die;

step 2, on the basis that the finish forging die is qualified, reducing the pre-torsion angle compensation of each section blade body profile to 1/2 of the original pre-torsion angle compensation size to form a 1 st version correction die, and using the 1 st version correction die to heat the forge piece and correct the pressure test;

step 3, measuring torsion angle deviation delta alpha of the size of each section of the forged piece after pressure test and the theoretical size and contour deviation delta b1, delta b2 after torsion angle fitting 8230, 8230;

step 4, according to the torsion angle deviation, the mould line of the correction mould correspondingly rotates delta alpha, and the rotation center is the mass center of the theoretical line;

step 5, sequentially taking a plurality of points on a single spline curve of a section molded line of the correcting die, outputting point coordinates, adjusting delta b1 and delta b2 (8230) ' delta b1 and delta b2 (8230) ' delta b 30) according to contour deviations delta b1 and delta b2 (8230) ' Y values of corresponding point coordinates, making a new spline curve after adjustment, and then performing curve smoothing to form a correcting die of version 2;

and 6, repeating the steps 3, 4 and 5 until the corrected size meets the requirement.

It should be noted that the meaning of the finish forging die in the foregoing step 1 and step 2 on the basis of passing is: the surface of the die does not need to be polished and repaired when the finish forging die is used for adjusting the die, and qualified forgings can be produced only by increasing and decreasing the gaskets up and down, left and right and front and back.

It should be noted that, in the foregoing step 1.2, the meaning of using boolean operation to make the trimming die on the basis of the finish forging die is: in modeling software (for example, UG), an operation instruction such as solid merging and trimming is performed for a 3D model (model) of a mold.

It should be noted that the profile deviation in the foregoing step 3 refers to a coordinate difference in the Y-axis direction by default.

Further, in the step 1, the trimming die is designed by using UG software.

Further, in the step 2, UG software is used to reduce the pre-twisted angle compensation of each section blade profile line to 1/2 of the original value to form a 1 st version of calibration model.

Further, in the step 3, the torsion angle deviation delta alpha of the size of each section of the forged piece after pressure test and the theoretical size and the contour deviation delta b1, delta b2, 8230and 8230after torsion angle fitting are measured by three coordinates.

Further, in the step 5, a plurality of points are taken on the single spline curve of the section molded line of the correction die according to the sequence of equal arc length.

Alternatively, the number of points taken on a single spline curve of the section molded line of the correction die according to the sequence of equal arc lengths is more than or equal to 100.

The existing correction die design method is not suitable for correcting the precise small-allowance blade forging, and the correction size deviation is large.

Compared with the existing design method of the correcting die, the method fully considers the local plastic deformation and the elastic deformation in the correcting process, compensates the deformation during the design and optimization of the die, improves the dimensional precision of a correcting piece, and can be used for correcting the precise small-allowance blade forging.

In addition, because the invention is carried out on the basis that the finish forging die is qualified when designing the correcting die, the upper, lower, left, right, front and back gaskets of the die are only required to be adjusted when adjusting the die during the die version iteration, and the trimming of the die surface is not involved, the die does not need to be repaired when the product is produced on site by the correcting die which is designed and optimized by the invention, and the production efficiency is improved.

Drawings

FIG. 1 is a schematic three-dimensional measurement of a blade forging according to the present invention;

FIG. 2 is a schematic diagram of the pre-twist angle optimization of the calibration mold according to the present invention;

FIG. 3 is a schematic diagram of the profile optimization of the calibration mold according to the present invention;

FIG. 4 is a schematic view of a trimming die of the present invention;

FIG. 5 is a schematic diagram of a calibration mold according to the present invention.

Detailed Description

The present invention will be further described with reference to the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter of the present invention is limited to the following embodiments, and various modifications, substitutions and alterations made based on the common technical knowledge and conventional means in the art without departing from the technical idea of the present invention are included in the scope of the present invention.

As shown in fig. 1 to 5, the method for designing and optimizing the aero-engine precision small margin blade calibration mold adopted by the present invention comprises the following steps:

step 1: on the basis that the finish forging die is qualified, UG software is used for designing a trimming die, and the trimming die is designed by the following steps:

step 1.1: canceling the forging springback deformation pre-torsion angle compensation of the blade profile of each section of the finish forging die;

step 1.2: utilizing Boolean operation to make a trimming die on the basis of a finish forging die;

as shown in fig. 4, the trimming die designed by the above steps has small thermal trimming deformation, and is beneficial to correction, and then the trimming die is used for trimming the finish forged piece;

and 2, step: on the basis that the finish forging die is qualified, UG software is used for reducing the pre-torsion angle compensation of each section blade body type line to 1/2 of the original pre-torsion angle compensation size to form a 1 st version of correction die, as shown in FIG. 5;

and 3, step 3: the 1 st edition of correction die shown in FIG. 5 is adopted to heat and correct the pressure test of the forge piece, and the torsion angle deviation delta alpha between the size of each section of the forge piece after the pressure test and the theoretical size and the contour deviation delta b1 and delta b2 after the torsion angle fitting are measured by three coordinates, 8230, which is shown in FIG. 1;

and 4, step 4: according to the torsion angle deviation, the molded line of the correction die correspondingly rotates by-delta alpha, and the rotation center is the centroid of the theoretical molded line, as shown in fig. 2;

and 5: 100 points are taken on a single spline curve of the section molded line of the correction die according to equal arc length, point coordinates are output, a new spline curve is made after adjustment according to contour deviation delta b1, delta b2 \8230 \ 8230 \ corresponding point coordinate Y values are adjusted-delta b1, -delta b2 \8230 \ 8230 \, and then curve smoothing is carried out as shown in figure 3, so that the 2 nd version of correction die design is completed.

And 5: and (5) repeating the steps (3), (4) and (5) until the corrected size meets the requirement.

Those matters not described in detail in the description of the invention are well within the knowledge of a person skilled in the art in the prior art. Although illustrative embodiments of the present invention have been described above to facilitate the understanding of the present invention by those skilled in the art, it should be understood that the present invention is not limited to the scope of the embodiments, and various changes may be made apparent to those skilled in the art as long as they are within the spirit and scope of the present invention as defined and defined by the appended claims, and all matters of the invention which utilize the inventive concepts are protected.

Claims

1. The design and optimization method of the aeroengine precision small-allowance blade correcting die is characterized by comprising the following steps: comprises the following steps of (a) carrying out,

step 1, designing a trimming die on the basis of qualified finish forging die, and specifically comprising the following steps:

step 1.1, canceling forging springback deformation pre-torsion angle compensation of blade profile lines of each section of the finish forging die;

step 5, sequentially taking a plurality of points on a single spline curve of the cross-section molded line of the correction die, outputting point coordinates, adjusting delta b1 and delta b2 (8230) \ 8230corresponding to the point coordinate Y value, adjusting delta b1 and delta b2 (8230) \ 8230;, making a new spline curve after adjustment, and then performing curve smoothing to form a 2 nd version correction die;

2. The design and optimization method of the aeroengine precision small margin blade correction die as claimed in claim 1, characterized in that: in the step 1, UG software is used for designing the trimming die.

3. The design and optimization method of the aeroengine precision small margin blade correction die as claimed in claim 1, characterized in that: in the step 2, UG software is used for reducing the pre-torsion angle compensation of each section blade profile line to 1/2 of the original pre-torsion angle compensation value to form a 1 st version of correction die.

4. The design and optimization method of the aeroengine precision small margin blade correction die as claimed in claim 1, characterized in that: in the step 3, the torsion angle deviation delta alpha of the size of each section of the forged piece after pressure test and the theoretical size and the contour deviation delta b1, delta b2 after torsion angle fitting 8230, 8230and the like are measured by three coordinates.

5. The design and optimization method of the aeroengine precision small margin blade correction die as claimed in claim 1, characterized in that: in the step 5, a plurality of points are taken on the single spline curve of the section molded line of the correction die according to the equal arc length sequence.